Airfoil shape for a compressor

ABSTRACT

An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in a scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

RELATED APPLICATIONS

The present application is related to the following commonly assigned applications: Ser. No. 14/845,337; Ser. No. 14/845,347; Ser. No. 14/845,347; Ser. No. 14/845,370; Ser. No. 14/845,360; Ser. No. 14/845,378; Ser. No. 14/845,388; Ser. No. 14/845,398; Ser. No. 14/845,411; Ser. No. 14/845,421, filed concurrently herewith.

TECHNICAL FIELD

The present application and the resultant patent relate generally to gas turbine engines and more particularly relates to an airfoil profile or airfoil shape for use in a compressor.

BACKGROUND OF THE INVENTION

In a gas turbine engine, many system requirements should be met at each stage of the flow path therethrough to meet design goals. These design goals include, but are not limited to, overall improved efficiency, a reduction in vibratory response, improved airfoil loading capability, and the like. For example, a compressor airfoil profile should achieve thermal and mechanical operating requirements for a particular stage in the compressor. Moreover, component lifetime, reliability, and cost targets also should be met.

SUMMARY OF THE INVENTION

According to one aspect of the present application, an article of manufacture is provided with a nominal airfoil profile substantially in accordance with the Cartesian coordinate values of X, Y, and Z set forth in scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.

According to another aspect of the present application, an article of manufacture is provided with a suction-side nominal airfoil profile substantially in accordance with the suction-side Cartesian coordinate values of X, Y, and Z set forth in scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined smoothly with one another to form a complete suction-side airfoil shape, the X, Y, and Z coordinate values being scalable as a function of the number to provide at least one of a non-scaled, scaled-up, and scaled-down airfoil profile.

According to yet another aspect of the present application, a compressor is provided with a number of rotor blades, each of the rotor blades including an airfoil having a suction-side airfoil shape, the airfoil having a nominal profile substantially in accordance with the suction-side Cartesian coordinate values of X, Y, and Z set forth in scalable TABLE 1, wherein the Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete suction-side airfoil shape.

These and other features and improvements of the present application and the resultant patent will become apparent to one of ordinary skill in the art upon review of the following detailed description when taken in conjunction with the several drawings and the appended claims.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a schematic diagram of a gas turbine engine including a compressor, a combustor, a turbine, and a load.

FIG. 2 is a schematic diagram of a compressor with multiple stages and a flow path therethrough.

FIG. 3 is a perspective view of a rotor blade airfoil as may be described herein.

FIG. 4 is a cross-sectional view of the rotor blade airfoil taken along line 4-4 of FIG. 3.

DETAILED DESCRIPTION

Referring now to the drawings, in which like numerals refer to like elements throughout the several views, FIG. 1 shows a schematic view of gas turbine engine 10 as may be used herein. The gas turbine engine 10 may include a compressor 15. The compressor 15 compresses an incoming flow of air 20. The compressor 15 delivers the compressed flow of air 20 to a combustor 25. The combustor 25 mixes the compressed flow of air 20 with a pressurized flow of fuel 30 and ignites the mixture to create a flow of combustion gases 35. Although only a single combustor 25 is shown, the gas turbine engine 10 may include any number of the combustors 25 arranged in a circumferential array or otherwise. The flow of combustion gases 35 is delivered in turn to a turbine 40. The flow of combustion gases 35 drives the turbine 40 so as to produce mechanical work. The mechanical work produced in the turbine 40 drives the compressor 15 via a shaft 45 and an external load 50 such as an electrical generator and the like.

The gas turbine engine 10 may use natural gas, liquid fuels, various types of syngas, and/or other types of fuels and blends thereof. The gas turbine engine 10 may be any one of a number of different gas turbine engines offered by General Electric Company of Schenectady, N.Y., including, but not limited to, those such as a 7 or a 9 series heavy duty gas turbine engine and the like. The gas turbine engine 10 may have different configurations and may use other types of components. Other types of gas turbine engines also may be used herein. Multiple gas turbine engines, other types of turbines, and other types of power generation equipment also may be used herein together.

FIG. 2 shows an example of the compressor 15. The compressor 15 may include a number of compressor stages with an axial compressor flow path 55 therethrough. As one non-limiting example only, the compressor flow path 55 may include about eighteen rotor/stator stages. The exact number of rotor and stator stages, however, may be a matter of engineering design choice and may be more or less than the illustrated eighteen stages. It is to be understood that any number of rotor and stator stages may be provided herein.

Each stage of the compressor 15 may include a number of circumferentially spaced rotor blades 60 mounted on a rotor wheel 65 and a number of circumferentially spaced stator vanes 70 attached to a static compressor case 75. Each of the rotor wheels 65 may be attached to an aft drive shaft 80, which may be connected to the turbine section of the engine. The rotor blades and stator vanes may lie in the flow path 55 of the compressor 15. The direction of airflow through the compressor flow path 55 flows generally from left to right in FIG. 2. Other components and other configurations may be used herein.

The compressor rotor blades 60 impart kinetic energy to the airflow and therefore bring about a desired pressure rise. Directly following the rotor blades 60 may be a stage of the compressor stator vanes 70. However, in some designs the stator vanes may precede the rotor blades. Both the rotor blades and stator vanes turn the airflow, slow the airflow velocity (in the respective airfoil frame of reference), and yield a rise in the static pressure of the airflow. Typically, multiple rows of rotor/stator stages are arranged in axial flow compressors to achieve a desired discharge to inlet pressure ratio. Each rotor blade and stator vane includes an airfoil, and these airfoils can be secured to rotor wheels or a stator case by an appropriate attachment configuration, often known as a “root,” “base” or “dovetail”. In addition, the compressor 15 also may include inlet guide vanes (IGV's) 85, variable stator vanes (VSV's) 90, and exit or exhaust guide vanes (EGV's) 95. All of these blades and vanes have airfoils that act on the medium (e.g., air) passing through the compressor flow path 55. Other components and other configurations may be used herein.

The rotor blades 60 and stator vanes 70 are merely exemplary of the stages of the compressor 15 described herein. In addition, each rotor blade 60, stator vane 70, inlet guide vane 85, variable stator vane 90, and exit guide vane 95 may be considered an article of manufacture. Further, the article of manufacture may include a rotor blade configured for use with a compressor 15.

FIG. 3 shows an example of a rotor blade 100 as may be described herein. In this example, the rotor blade 100 includes an airfoil 105. Each of the rotor blades 100 may have an airfoil profile at any cross-section from an airfoil root 110 to an airfoil tip 120. The airfoil 105 may connect to a mounting base 130, which also may be referred to as a dovetail. The mounting base 130 fits into a complementary shaped groove or slot in the rotor or rotor wheel 65. Examples of the compressor 15 may include a variety of blades 60 and vanes 70, 85, 90, 95 arranged in multiple stages.

Referring to FIG. 4, the airfoil 105 may have a suction side 140 and a pressure side 150. The suction side 140 may be located on the opposing side of the airfoil 105 from the pressure side 150. Thus, each rotor blade 60 may have an airfoil profile at any cross-section in the shape of the airfoil 105. The airfoil 105 also may include a leading edge 160 and a trailing edge 170 and with a chord length 180 extending therebetween. The root 110 of the airfoil 105 corresponds to the lowest non-dimensional Z value of scalable TABLE 1. The tip 120 of the airfoil 105 corresponds to the highest non-dimensional Z value of scalable TABLE 1. An airfoil 105 may extend beyond the compressor flowpath and may be tipped to achieve the desired endwall clearances. By way of example only, the airfoil may have a height from about one (1) inch to about twenty (20) inches (about 2.54 centimeters to about 50.8 centimeters) or more. Any specific airfoil height may be used herein as desired in a specific application. Other components and other configurations may be used herein.

The compressor flow path 55 requires airfoils 105 that meet system requirements of aerodynamic and mechanical blade/vane loading and efficiency. For example, it is desirable that the airfoils 105 are designed to reduce the vibratory response or vibratory stress response of the respective blades and/or vanes. Materials such as high strength alloys, non-corrosive alloys, and/or stainless steels may be used in the blades and/or vanes. To define the airfoil shape of each blade airfoil and/or vane airfoil, there is a unique set or loci of points in space that meet the stage requirements and can be manufactured. These unique loci of points meet the requirements for stage efficiency and may be arrived at by iteration between aerodynamic and mechanical loadings so as to enable the turbine and compressor to run in an efficient, safe, reliable, and smooth manner. These points are unique and specific to the system. The locus that defines the airfoil profile includes a set of points with X, Y, and Z coordinates relative to a reference origin coordinate system. The three-dimensional Cartesian coordinate system of X, Y, and Z values given in scalable TABLE 1 below defines the profile of the rotor blade airfoil at various locations along its length. The scalable TABLE 1 lists data for a non-coated airfoil. The envelope/tolerance for the coordinates may be about +/−5% of the chord length 180 in a direction normal to any airfoil surface location or about +/−0.25 inches (about 6.36 millimeters) in a direction normal to any airfoil surface location. However, tolerances of about +/−0.15 inches to about +/−0.25 inches (about 6.36 millimeters), or about +/−3% to about +/−5% in a direction normal to an airfoil surface location may also be used, as desired in the specific application.

A point data origin 190 may be the mid-point of the suction or pressure side of the base or tip of the airfoil, the leading edge or trailing edge of the base of the airfoil, or any other suitable location as desired. The coordinate values for the X, Y, and Z coordinates are set forth in non-dimensionalized units in scalable TABLE 1, although other units of dimensions may be used when the values are appropriately converted. As one example only, the Cartesian coordinate values of X, Y, and Z may be convertible to dimensional distances by multiplying the X, Y, and Z values by a constant number (e.g., 100). The number, used to convert the non-dimensional values to dimensional distances, may be a fraction (e.g., ½, ¼, etc.), decimal fraction (e.g., 0.5, 1.5, 10.25, etc.), integer (e.g., 1, 2, 10, 100, etc.), a mixed number (e.g., 11/2, 101/4, etc.), and the like. The dimensional distances may be in any suitable format (e.g., inches, feet, millimeters, centimeters, meters, etc.) As one non-limiting example only, the Cartesian coordinate system has orthogonally-related X, Y, and Z axes and the X axis may lie generally parallel to the compressor rotor centerline, i.e., the rotary axis and a positive X coordinate value is axial toward the aft, i.e., exhaust end of the turbine. The positive Y coordinate value extends tangentially in the direction of rotation of the rotor and the positive Z coordinate value is radially outwardly toward the rotor blade tip or stator vane base. All the values in scalable TABLE 1 are given at room temperature and are unfilleted.

By defining X and Y coordinate values at selected locations in a Z direction (or height) normal to the X, Y plane, the profile section or airfoil shape of the airfoil, at each Z height along the length of the airfoil may be ascertained. By connecting the X and Y values with smooth continuing arcs, each profile section at each Z height may be fixed. The airfoil profiles of the various surface locations between each Z height may be determined by smoothly connecting the adjacent profile sections to one another to form the airfoil profile.

The values in TABLE 1 may be generated and shown from zero to four or more decimal places for determining the profile of the airfoil. As the airfoil heats up the associated stress and temperature may cause a change in the X, Y, and Z values. Accordingly, the values for the profile given in TABLE 1 represent ambient, non-operating or non-hot conditions (e.g., room temperature) and may be for an uncoated airfoil.

There are typical manufacturing tolerances as well as optional coatings which may be accounted for in the actual profile of the airfoil. Each section may be joined smoothly with the other sections to form the complete airfoil shape. It will therefore be appreciated that +/− typical manufacturing tolerances, i.e., +/− values, including any coating thicknesses, are additive to the X and Y values given in TABLE 1 below. Accordingly, a distance of about +/−5% of chord length and/or +/−0.25 inches (about 6.36 millimeters) in a direction normal to a surface location along the airfoil profile defines an airfoil profile envelope for this particular airfoil design and compressor, i.e., a range of variation between measured points on the actual airfoil surface at nominal cold or room temperature and the ideal position of those points as given in the TABLE 1 below at the same temperature. Additionally, a distance of about +/−5% of a chord length in a direction normal to an airfoil surface location along the airfoil profile also may define an airfoil profile envelope for this particular airfoil design. The data is scalable and the geometry pertains to all aerodynamic scales, at, above and/or below about 3,000 RPM. The rotor blade airfoil design is robust to this range of variation without impairment of mechanical and aerodynamic functions.

The coordinate values given in scalable TABLE 1 below provide the nominal profile for exemplary stages of a compressor rotor blade. Specifically, a first stage rotor blade of, for example, a 9HA.01 compressor and the like:

TABLE 1 PRESSURE SIDE SUCTION SIDE X Y Z X Y Z −6.6608 3.8034 −2.5267 5.6595 −0.3581 −2.5267 −6.6586 3.8051 −2.5267 5.6619 −0.3807 −2.5267 −6.6542 3.8082 −2.5267 5.6616 −0.4108 −2.5267 −6.6445 3.8131 −2.5267 5.6558 −0.4482 −2.5267 −6.6233 3.8175 −2.5267 5.6411 −0.4908 −2.5267 −6.5896 3.8152 −2.5267 5.6089 −0.5416 −2.5267 −6.5313 3.7984 −2.5267 5.5474 −0.5892 −2.5267 −6.4582 3.7654 −2.5267 5.4570 −0.6268 −2.5267 −6.3642 3.7133 −2.5267 5.3465 −0.6711 −2.5267 −6.2505 3.6423 −2.5267 5.2147 −0.7227 −2.5267 −6.1054 3.5457 −2.5267 5.0600 −0.7821 −2.5267 −5.9398 3.4316 −2.5267 4.8766 −0.8507 −2.5267 −5.7638 3.3090 −2.5267 4.6641 −0.9270 −2.5267 −5.5657 3.1709 −2.5267 4.4221 −1.0101 −2.5267 −5.3457 3.0176 −2.5267 4.1500 −1.0987 −2.5267 −5.1039 2.8486 −2.5267 3.8469 −1.1891 −2.5267 −4.8511 2.6719 −2.5267 3.5133 −1.2771 −2.5267 −4.5874 2.4874 −2.5267 3.1636 −1.3559 −2.5267 −4.3115 2.2972 −2.5267 2.7977 −1.4251 −2.5267 −4.0224 2.1029 −2.5267 2.4156 −1.4835 −2.5267 −3.7199 1.9048 −2.5267 2.0170 −1.5289 −2.5267 −3.4034 1.7040 −2.5267 1.6017 −1.5587 −2.5267 −3.0717 1.5026 −2.5267 1.1691 −1.5697 −2.5267 −2.7236 1.3023 −2.5267 0.7188 −1.5588 −2.5267 −2.3693 1.1122 −2.5267 0.2687 −1.5242 −2.5267 −2.0080 0.9340 −2.5267 −0.1755 −1.4662 −2.5267 −1.6401 0.7689 −2.5267 −0.6136 −1.3849 −2.5267 −1.2663 0.6174 −2.5267 −1.0456 −1.2807 −2.5267 −0.8876 0.4793 −2.5267 −1.4718 −1.1538 −2.5267 −0.5042 0.3542 −2.5267 −1.8919 −1.0042 −2.5267 −0.1168 0.2425 −2.5267 −2.3062 −0.8320 −2.5267 0.2739 0.1440 −2.5267 −2.7135 −0.6366 −2.5267 0.6667 0.0580 −2.5267 −3.1074 −0.4201 −2.5267 1.0613 −0.0162 −2.5267 −3.4865 −0.1832 −2.5267 1.4574 −0.0801 −2.5267 −3.8510 0.0739 −2.5267 1.8418 −0.1328 −2.5267 −4.1898 0.3412 −2.5267 2.2141 −0.1754 −2.5267 −4.5047 0.6163 −2.5267 2.5744 −0.2085 −2.5267 −4.7982 0.8954 −2.5267 2.9225 −0.2331 −2.5267 −5.0710 1.1751 −2.5267 3.2577 −0.2500 −2.5267 −5.3210 1.4532 −2.5267 3.5796 −0.2611 −2.5267 −5.5525 1.7264 −2.5267 3.8883 −0.2674 −2.5267 −5.7657 1.9947 −2.5267 4.1703 −0.2686 −2.5267 −5.9596 2.2590 −2.5267 4.4254 −0.2654 −2.5267 −6.1277 2.5051 −2.5267 4.6536 −0.2584 −2.5267 −6.2721 2.7318 −2.5267 4.8548 −0.2485 −2.5267 −6.3940 2.9381 −2.5267 5.0290 −0.2376 −2.5267 −6.5011 3.1368 −2.5267 5.1764 −0.2274 −2.5267 −6.5859 3.3147 −2.5267 5.3023 −0.2178 −2.5267 −6.6426 3.4555 −2.5267 5.4081 −0.2090 −2.5267 −6.6786 3.5715 −2.5267 5.4951 −0.2022 −2.5267 −6.6951 3.6609 −2.5267 5.5629 −0.2178 −2.5267 −6.6952 3.7291 −2.5267 5.6068 −0.2496 −2.5267 −6.6863 3.7660 −2.5267 5.6318 −0.2817 −2.5267 −6.6750 3.7874 −2.5267 5.6470 −0.3122 −2.5267 −6.6674 3.7971 −2.5267 5.6554 −0.3380 −2.5267 −6.6631 3.8014 −2.5267 −6.5923 3.9165 −1.6804 5.6078 −0.5331 −1.6804 −6.5901 3.9182 −1.6804 5.6095 −0.5556 −1.6804 −6.5856 3.9212 −1.6804 5.6082 −0.5855 −1.6804 −6.5758 3.9257 −1.6804 5.6009 −0.6223 −1.6804 −6.5545 3.9293 −1.6804 5.5843 −0.6639 −1.6804 −6.5210 3.9259 −1.6804 5.5493 −0.7125 −1.6804 −6.4635 3.9073 −1.6804 5.4852 −0.7555 −1.6804 −6.3913 3.8724 −1.6804 5.3941 −0.7887 −1.6804 −6.2988 3.8184 −1.6804 5.2829 −0.8280 −1.6804 −6.1866 3.7456 −1.6804 5.1502 −0.8737 −1.6804 −6.0434 3.6468 −1.6804 4.9946 −0.9262 −1.6804 −5.8798 3.5307 −1.6804 4.8103 −0.9868 −1.6804 −5.7058 3.4062 −1.6804 4.5968 −1.0540 −1.6804 −5.5098 3.2661 −1.6804 4.3538 −1.1272 −1.6804 −5.2920 3.1108 −1.6804 4.0809 −1.2046 −1.6804 −5.0525 2.9395 −1.6804 3.7779 −1.2827 −1.6804 −4.8025 2.7602 −1.6804 3.4449 −1.3573 −1.6804 −4.5416 2.5732 −1.6804 3.0961 −1.4225 −1.6804 −4.2687 2.3799 −1.6804 2.7318 −1.4777 −1.6804 −3.9828 2.1822 −1.6804 2.3515 −1.5216 −1.6804 −3.6838 1.9801 −1.6804 1.9553 −1.5526 −1.6804 −3.3710 1.7747 −1.6804 1.5428 −1.5676 −1.6804 −3.0433 1.5677 −1.6804 1.1138 −1.5638 −1.6804 −2.6995 1.3607 −1.6804 0.6678 −1.5382 −1.6804 −2.3497 1.1632 −1.6804 0.2232 −1.4901 −1.6804 −1.9938 0.9773 −1.6804 −0.2149 −1.4196 −1.6804 −1.6319 0.8039 −1.6804 −0.6467 −1.3269 −1.6804 −1.2639 0.6431 −1.6804 −1.0722 −1.2124 −1.6804 −0.8905 0.4947 −1.6804 −1.4914 −1.0766 −1.6804 −0.5124 0.3586 −1.6804 −1.9043 −0.9189 −1.6804 −0.1297 0.2359 −1.6804 −2.3109 −0.7395 −1.6804 0.2568 0.1262 −1.6804 −2.7105 −0.5374 −1.6804 0.6457 0.0292 −1.6804 −3.0964 −0.3145 −1.6804 1.0369 −0.0560 −1.6804 −3.4671 −0.0715 −1.6804 1.4300 −0.1308 −1.6804 −3.8227 0.1910 −1.6804 1.8117 −0.1942 −1.6804 −4.1526 0.4627 −1.6804 2.1818 −0.2470 −1.6804 −4.4591 0.7409 −1.6804 2.5401 −0.2902 −1.6804 −4.7450 1.0215 −1.6804 2.8863 −0.3245 −1.6804 −5.0121 1.3019 −1.6804 3.2197 −0.3508 −1.6804 −5.2584 1.5806 −1.6804 3.5401 −0.3710 −1.6804 −5.4875 1.8543 −1.6804 3.8474 −0.3863 −1.6804 −5.6996 2.1227 −1.6804 4.1282 −0.3962 −1.6804 −5.8931 2.3871 −1.6804 4.3824 −0.4010 −1.6804 −6.0612 2.6333 −1.6804 4.6100 −0.4015 −1.6804 −6.2054 2.8596 −1.6804 4.8107 −0.3984 −1.6804 −6.3267 3.0649 −1.6804 4.9846 −0.3937 −1.6804 −6.4328 3.2617 −1.6804 5.1317 −0.3887 −1.6804 −6.5164 3.4366 −1.6804 5.2575 −0.3837 −1.6804 −6.5724 3.5749 −1.6804 5.3631 −0.3787 −1.6804 −6.6081 3.6886 −1.6804 5.4500 −0.3752 −1.6804 −6.6248 3.7764 −1.6804 5.5164 −0.3931 −1.6804 −6.6255 3.8434 −1.6804 5.5585 −0.4254 −1.6804 −6.6171 3.8795 −1.6804 5.5824 −0.4574 −1.6804 −6.6062 3.9008 −1.6804 5.5967 −0.4875 −1.6804 −6.5988 3.9103 −1.6804 5.6044 −0.5132 −1.6804 −6.5945 3.9145 −1.6804 −6.5242 4.0270 −0.8341 5.5561 −0.7081 −0.8341 −6.5221 4.0286 −0.8341 5.5571 −0.7304 −0.8341 −6.5176 4.0316 −0.8341 5.5548 −0.7598 −0.8341 −6.5076 4.0361 −0.8341 5.5461 −0.7960 −0.8341 −6.4864 4.0391 −0.8341 5.5275 −0.8364 −0.8341 −6.4530 4.0349 −0.8341 5.4902 −0.8822 −0.8341 −6.3961 4.0152 −0.8341 5.4243 −0.9206 −0.8341 −6.3246 3.9792 −0.8341 5.3326 −0.9495 −0.8341 −6.2330 3.9240 −0.8341 5.2209 −0.9838 −0.8341 −6.1221 3.8498 −0.8341 5.0875 −1.0235 −0.8341 −5.9806 3.7495 −0.8341 4.9313 −1.0691 −0.8341 −5.8189 3.6314 −0.8341 4.7463 −1.1214 −0.8341 −5.6469 3.5047 −0.8341 4.5320 −1.1794 −0.8341 −5.4535 3.3622 −0.8341 4.2885 −1.2424 −0.8341 −5.2386 3.2038 −0.8341 4.0153 −1.3085 −0.8341 −5.0022 3.0295 −0.8341 3.7127 −1.3743 −0.8341 −4.7552 2.8473 −0.8341 3.3805 −1.4357 −0.8341 −4.4970 2.6576 −0.8341 3.0331 −1.4872 −0.8341 −4.2270 2.4616 −0.8341 2.6704 −1.5286 −0.8341 −3.9444 2.2603 −0.8341 2.2924 −1.5584 −0.8341 −3.6489 2.0542 −0.8341 1.8989 −1.5750 −0.8341 −3.3399 1.8443 −0.8341 1.4898 −1.5755 −0.8341 −3.0163 1.6320 −0.8341 1.0648 −1.5574 −0.8341 −2.6769 1.4190 −0.8341 0.6238 −1.5177 −0.8341 −2.3325 1.2148 −0.8341 0.1845 −1.4565 −0.8341 −1.9820 1.0212 −0.8341 −0.2486 −1.3740 −0.8341 −1.6252 0.8391 −0.8341 −0.6755 −1.2702 −0.8341 −1.2625 0.6692 −0.8341 −1.0962 −1.1453 −0.8341 −0.8947 0.5111 −0.8341 −1.5109 −0.9994 −0.8341 −0.5217 0.3649 −0.8341 −1.9191 −0.8320 −0.8341 −0.1440 0.2313 −0.8341 −2.3206 −0.6425 −0.8341 0.2380 0.1107 −0.8341 −2.7102 −0.4330 −0.8341 0.6231 0.0025 −0.8341 −3.0854 −0.2039 −0.8341 1.0106 −0.0939 −0.8341 −3.4466 0.0446 −0.8341 1.4005 −0.1799 −0.8341 −3.7942 0.3118 −0.8341 1.7794 −0.2540 −0.8341 −4.1177 0.5872 −0.8341 2.1470 −0.3173 −0.8341 −4.4191 0.8684 −0.8341 2.5033 −0.3707 −0.8341 −4.7005 1.1513 −0.8341 2.8474 −0.4148 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−2.2629 2.0575 20.7496 0.4722 −1.7314 20.7496 −2.4784 2.4258 20.7496 0.6773 −2.0864 20.7496 −2.6856 2.7823 20.7496 0.8765 −2.4284 20.7496 −2.8849 3.1271 20.7496 1.0708 −2.7569 20.7496 −3.0758 3.4602 20.7496 1.2606 −3.0716 20.7496 −3.2583 3.7819 20.7496 1.4459 −3.3724 20.7496 −3.4323 4.0918 20.7496 1.6267 −3.6595 20.7496 −3.5975 4.3905 20.7496 1.8035 −3.9323 20.7496 −3.7532 4.6782 20.7496 1.9684 −4.1793 20.7496 −3.9001 4.9544 20.7496 2.1194 −4.4016 20.7496 −4.0312 5.2069 20.7496 2.2555 −4.5997 20.7496 −4.1473 5.4350 20.7496 2.3760 −4.7742 20.7496 −4.2489 5.6387 20.7496 2.4816 −4.9247 20.7496 −4.3422 5.8305 20.7496 2.5726 −5.0509 20.7496 −4.4197 5.9984 20.7496 2.6507 −5.1584 20.7496 −4.4755 6.1292 20.7496 2.7158 −5.2492 20.7496 −4.5162 6.2355 20.7496 2.7690 −5.3241 20.7496 −4.5429 6.3164 20.7496 2.8111 −5.3844 20.7496 −4.5591 6.3784 20.7496 2.8433 −5.4309 20.7496 −4.5649 6.4134 20.7496 2.8673 −5.4658 20.7496 −4.5655 6.4362 20.7496 2.8870 −5.4952 20.7496 −4.5630 6.4473 20.7496 2.8909 −5.5227 20.7496 −4.5600 6.4521 20.7496 −4.5602 6.5718 21.1732 2.7909 −5.6095 21.1732 −4.5574 6.5724 21.1732 2.7724 −5.6198 21.1732 −4.5520 6.5708 21.1732 2.7452 −5.6140 21.1732 −4.5427 6.5641 21.1732 2.7168 −5.5917 21.1732 −4.5271 6.5475 21.1732 2.6833 −5.5643 21.1732 −4.5053 6.5193 21.1732 2.6392 −5.5271 21.1732 −4.4697 6.4658 21.1732 2.5825 −5.4779 21.1732 −4.4257 6.3926 21.1732 2.5127 −5.4152 21.1732 −4.3699 6.2933 21.1732 2.4300 −5.3371 21.1732 −4.3020 6.1679 21.1732 2.3347 −5.2409 21.1732 −4.2137 6.0051 21.1732 2.2265 −5.1253 21.1732 −4.1105 5.8180 21.1732 2.1004 −4.9867 21.1732 −3.9988 5.6192 21.1732 1.9587 −4.8240 21.1732 −3.8711 5.3967 21.1732 1.8054 −4.6344 21.1732 −3.7269 5.1509 21.1732 1.6410 −4.4178 21.1732 −3.5660 4.8818 21.1732 1.4657 −4.1741 21.1732 −3.3957 4.6017 21.1732 1.2801 −3.9030 21.1732 −3.2161 4.3107 21.1732 1.0926 −3.6158 21.1732 −3.0278 4.0082 21.1732 0.9029 −3.3129 21.1732 −2.8313 3.6941 21.1732 0.7107 −2.9944 21.1732 −2.6266 3.3683 21.1732 0.5151 −2.6610 21.1732 −2.4143 3.0304 21.1732 0.3153 −2.3132 21.1732 −2.1946 2.6804 21.1732 0.1099 −1.9521 21.1732 −1.9677 2.3181 21.1732 −0.1022 −1.5784 21.1732 −1.7409 1.9557 21.1732 −0.3156 −1.2053 21.1732 −1.5147 1.5929 21.1732 −0.5304 −0.8332 21.1732 −1.2891 1.2297 21.1732 −0.7467 −0.4619 21.1732 −1.0644 0.8660 21.1732 −0.9642 −0.0913 21.1732 −0.8409 0.5015 21.1732 −1.1827 0.2788 21.1732 −0.6192 0.1360 21.1732 −1.4013 0.6487 21.1732 −0.3997 −0.2308 21.1732 −1.6199 1.0188 21.1732 −0.1828 −0.5992 21.1732 −1.8378 1.3891 21.1732 0.0314 −0.9693 21.1732 −2.0551 1.7600 21.1732 0.2428 −1.3407 21.1732 −2.2713 2.1314 21.1732 0.4522 −1.7134 21.1732 −2.4864 2.5034 21.1732 0.6534 −2.0744 21.1732 −2.6933 2.8636 21.1732 0.8479 −2.4228 21.1732 −2.8922 3.2120 21.1732 1.0367 −2.7579 21.1732 −3.0828 3.5484 21.1732 1.2206 −3.0795 21.1732 −3.2649 3.8734 21.1732 1.3996 −3.3875 21.1732 −3.4388 4.1864 21.1732 1.5741 −3.6817 21.1732 −3.6038 4.4881 21.1732 1.7445 −3.9617 21.1732 −3.7591 4.7786 21.1732 1.9032 −4.2154 21.1732 −3.9056 5.0577 21.1732 2.0494 −4.4434 21.1732 −4.0361 5.3127 21.1732 2.1816 −4.6464 21.1732 −4.1516 5.5433 21.1732 2.2986 −4.8253 21.1732 −4.2525 5.7491 21.1732 2.4010 −4.9796 21.1732 −4.3451 5.9430 21.1732 2.4896 −5.1091 21.1732 −4.4223 6.1125 21.1732 2.5657 −5.2193 21.1732 −4.4778 6.2446 21.1732 2.6294 −5.3120 21.1732 −4.5182 6.3518 21.1732 2.6814 −5.3887 21.1732 −4.5450 6.4334 21.1732 2.7228 −5.4503 21.1732 −4.5612 6.4958 21.1732 2.7544 −5.4977 21.1732 −4.5671 6.5312 21.1732 2.7780 −5.5334 21.1732 −4.5678 6.5540 21.1732 2.7974 −5.5633 21.1732 −4.5655 6.5652 21.1732 2.8009 −5.5910 21.1732 −4.5626 6.5701 21.1732 −4.5595 6.7187 21.6428 2.6695 −5.6953 21.6428 −4.5566 6.7193 21.6428 2.6511 −5.7053 21.6428 −4.5511 6.7174 21.6428 2.6239 −5.6989 21.6428 −4.5420 6.7104 21.6428 2.5958 −5.6757 21.6428 −4.5267 6.6931 21.6428 2.5625 −5.6473 21.6428 −4.5054 6.6641 21.6428 2.5188 −5.6087 21.6428 −4.4705 6.6095 21.6428 2.4628 −5.5576 21.6428 −4.4274 6.5348 21.6428 2.3940 −5.4926 21.6428 −4.3726 6.4336 21.6428 2.3124 −5.4114 21.6428 −4.3058 6.3061 21.6428 2.2190 −5.3117 21.6428 −4.2182 6.1408 21.6428 2.1132 −5.1916 21.6428 −4.1156 5.9509 21.6428 1.9902 −5.0479 21.6428 −4.0044 5.7493 21.6428 1.8529 −4.8787 21.6428 −3.8768 5.5239 21.6428 1.7060 −4.6814 21.6428 −3.7324 5.2749 21.6428 1.5490 −4.4564 21.6428 −3.5710 5.0026 21.6428 1.3815 −4.2038 21.6428 −3.4002 4.7191 21.6428 1.2052 −3.9228 21.6428 −3.2198 4.4245 21.6428 1.0277 −3.6255 21.6428 −3.0309 4.1184 21.6428 0.8479 −3.3126 21.6428 −2.8337 3.8004 21.6428 0.6647 −2.9849 21.6428 −2.6287 3.4705 21.6428 0.4767 −2.6430 21.6428 −2.4160 3.1282 21.6428 0.2833 −2.2875 21.6428 −2.1961 2.7735 21.6428 0.0835 −1.9191 21.6428 −1.9690 2.4064 21.6428 −0.1242 −1.5386 21.6428 −1.7423 2.0390 21.6428 −0.3337 −1.1591 21.6428 −1.5163 1.6712 21.6428 −0.5456 −0.7809 21.6428 −1.2912 1.3028 21.6428 −0.7596 −0.4038 21.6428 −1.0672 0.9338 21.6428 −0.9753 −0.0277 21.6428 −0.8448 0.5637 21.6428 −1.1921 0.3476 21.6428 −0.6245 0.1925 21.6428 −1.4096 0.7228 21.6428 −0.4067 −0.1803 21.6428 −1.6272 1.0977 21.6428 −0.1921 −0.5549 21.6428 −1.8445 1.4729 21.6428 0.0189 −0.9315 21.6428 −2.0611 1.8485 21.6428 0.2266 −1.3098 21.6428 −2.2769 2.2245 21.6428 0.4313 −1.6898 21.6428 −2.4918 2.6011 21.6428 0.6271 −2.0583 21.6428 −2.6986 2.9657 21.6428 0.8147 −2.4148 21.6428 −2.8974 3.3182 21.6428 0.9952 −2.7587 21.6428 −3.0879 3.6587 21.6428 1.1698 −3.0896 21.6428 −3.2698 3.9875 21.6428 1.3394 −3.4068 21.6428 −3.4436 4.3042 21.6428 1.5042 −3.7102 21.6428 −3.6085 4.6094 21.6428 1.6649 −3.9993 21.6428 −3.7636 4.9034 21.6428 1.8146 −4.2617 21.6428 −3.9097 5.1858 21.6428 1.9537 −4.4970 21.6428 −4.0397 5.4440 21.6428 2.0805 −4.7061 21.6428 −4.1544 5.6775 21.6428 2.1925 −4.8906 21.6428 −4.2543 5.8861 21.6428 2.2909 −5.0497 21.6428 −4.3460 6.0825 21.6428 2.3763 −5.1830 21.6428 −4.4224 6.2542 21.6428 2.4502 −5.2962 21.6428 −4.4773 6.3879 21.6428 2.5123 −5.3914 21.6428 −4.5174 6.4963 21.6428 2.5631 −5.4701 21.6428 −4.5438 6.5790 21.6428 2.6034 −5.5330 21.6428 −4.5599 6.6419 21.6428 2.6343 −5.5816 21.6428 −4.5659 6.6776 21.6428 2.6572 −5.6181 21.6428 −4.5668 6.7007 21.6428 2.6763 −5.6486 21.6428 −4.5646 6.7119 21.6428 2.6797 −5.6766 21.6428 −4.5618 6.7170 21.6428 −4.5502 6.8919 22.1132 2.5323 −5.7894 22.1132 −4.5474 6.8924 22.1132 2.5131 −5.7994 22.1132 −4.5420 6.8902 22.1132 2.4857 −5.7914 22.1132 −4.5330 6.8827 22.1132 2.4577 −5.7674 22.1132 −4.5180 6.8649 22.1132 2.4245 −5.7380 22.1132 −4.4972 6.8350 22.1132 2.3811 −5.6981 22.1132 −4.4633 6.7790 22.1132 2.3255 −5.6452 22.1132 −4.4214 6.7024 22.1132 2.2572 −5.5777 22.1132 −4.3681 6.5989 22.1132 2.1767 −5.4937 22.1132 −4.3025 6.4689 22.1132 2.0848 −5.3903 22.1132 −4.2163 6.3006 22.1132 1.9812 −5.2658 22.1132 −4.1146 6.1075 22.1132 1.8610 −5.1166 22.1132 −4.0039 5.9025 22.1132 1.7275 −4.9411 22.1132 −3.8765 5.6735 22.1132 1.5863 −4.7364 22.1132 −3.7317 5.4210 22.1132 1.4366 −4.5028 22.1132 −3.5695 5.1450 22.1132 1.2777 −4.2409 22.1132 −3.3977 4.8578 22.1132 1.1114 −3.9495 22.1132 −3.2164 4.5592 22.1132 0.9450 −3.6415 22.1132 −3.0265 4.2489 22.1132 0.7764 −3.3179 22.1132 −2.8287 3.9263 22.1132 0.6040 −2.9795 22.1132 −2.6229 3.5915 22.1132 0.4262 −2.6274 22.1132 −2.4098 3.2442 22.1132 0.2422 −2.2622 22.1132 −2.1895 2.8842 22.1132 0.0507 −1.8843 22.1132 −1.9621 2.5114 22.1132 −0.1497 −1.4947 22.1132 −1.7355 2.1382 22.1132 −0.3532 −1.1068 22.1132 −1.5100 1.7645 22.1132 −0.5600 −0.7207 22.1132 −1.2858 1.3897 22.1132 −0.7698 −0.3362 22.1132 −1.0634 1.0141 22.1132 −0.9821 0.0470 22.1132 −0.8431 0.6370 22.1132 −1.1964 0.4291 22.1132 −0.6255 0.2585 22.1132 −1.4119 0.8104 22.1132 −0.4113 −0.1220 22.1132 −1.6280 1.1915 22.1132 −0.2012 −0.5048 22.1132 −1.8443 1.5724 22.1132 0.0043 −0.8899 22.1132 −2.0603 1.9536 22.1132 0.2054 −1.2771 22.1132 −2.2759 2.3349 22.1132 0.4026 −1.6664 22.1132 −2.4908 2.7167 22.1132 0.5899 −2.0444 22.1132 −2.6976 3.0862 22.1132 0.7679 −2.4108 22.1132 −2.8965 3.4435 22.1132 0.9379 −2.7648 22.1132 −3.0871 3.7886 22.1132 1.1018 −3.1058 22.1132 −3.2690 4.1218 22.1132 1.2604 −3.4330 22.1132 −3.4430 4.4428 22.1132 1.4149 −3.7461 22.1132 −3.6079 4.7521 22.1132 1.5657 −4.0447 22.1132 −3.7630 5.0500 22.1132 1.7067 −4.3156 22.1132 −3.9089 5.3361 22.1132 1.8389 −4.5584 22.1132 −4.0383 5.5980 22.1132 1.9602 −4.7741 22.1132 −4.1520 5.8350 22.1132 2.0676 −4.9642 22.1132 −4.2507 6.0468 22.1132 2.1622 −5.1279 22.1132 −4.3408 6.2464 22.1132 2.2451 −5.2648 22.1132 −4.4157 6.4209 22.1132 2.3173 −5.3810 22.1132 −4.4696 6.5566 22.1132 2.3781 −5.4787 22.1132 −4.5089 6.6666 22.1132 2.4278 −5.5591 22.1132 −4.5347 6.7504 22.1132 2.4675 −5.6236 22.1132 −4.5505 6.8142 22.1132 2.4977 −5.6733 22.1132 −4.5564 6.8502 22.1132 2.5204 −5.7106 22.1132 −4.5573 6.8735 22.1132 2.5392 −5.7418 22.1132 −4.5554 6.8850 22.1132 2.5429 −5.7702 22.1132 −4.5525 6.8901 22.1132 −4.5275 7.0322 22.4422 2.4316 −5.8579 22.4422 −4.5246 7.0326 22.4422 2.4123 −5.8677 22.4422 −4.5192 7.0302 22.4422 2.3848 −5.8594 22.4422 −4.5104 7.0224 22.4422 2.3568 −5.8348 22.4422 −4.4957 7.0041 22.4422 2.3237 −5.8048 22.4422 −4.4754 6.9734 22.4422 2.2803 −5.7640 22.4422 −4.4424 6.9163 22.4422 2.2248 −5.7099 22.4422 −4.4017 6.8382 22.4422 2.1570 −5.6409 22.4422 −4.3497 6.7328 22.4422 2.0769 −5.5550 22.4422 −4.2855 6.6007 22.4422 1.9859 −5.4492 22.4422 −4.2006 6.4298 22.4422 1.8837 −5.3217 22.4422 −4.1001 6.2338 22.4422 1.7652 −5.1690 22.4422 −3.9902 6.0261 22.4422 1.6342 −4.9895 22.4422 −3.8634 5.7942 22.4422 1.4965 −4.7800 22.4422 −3.7186 5.5389 22.4422 1.3517 −4.5408 22.4422 −3.5561 5.2598 22.4422 1.1988 −4.2726 22.4422 −3.3839 4.9695 22.4422 1.0394 −3.9743 22.4422 −3.2019 4.6677 22.4422 0.8803 −3.6590 22.4422 −3.0117 4.3539 22.4422 0.7193 −3.3280 22.4422 −2.8136 4.0276 22.4422 0.5545 −2.9823 22.4422 −2.6078 3.6888 22.4422 0.3842 −2.6228 22.4422 −2.3947 3.3373 22.4422 0.2072 −2.2502 22.4422 −2.1747 2.9728 22.4422 0.0225 −1.8650 22.4422 −1.9478 2.5953 22.4422 −0.1715 −1.4681 22.4422 −1.7221 2.2171 22.4422 −0.3692 −1.0731 22.4422 −1.4979 1.8379 22.4422 −0.5707 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−0.8200 0.0247 24.5584 −0.9602 1.5236 24.5584 −0.9877 0.4657 24.5584 −0.7797 1.0890 24.5584 −1.1600 0.9051 24.5584 −0.6062 0.6516 24.5584 −1.3367 1.3430 24.5584 −0.4397 0.2114 24.5584 −1.5180 1.7790 24.5584 −0.2800 −0.2312 24.5584 −1.7033 2.2133 24.5584 −0.1267 −0.6761 24.5584 −1.8918 2.6461 24.5584 0.0212 −1.1229 24.5584 −2.0831 3.0777 24.5584 0.1639 −1.5712 24.5584 −2.2767 3.5082 24.5584 0.2972 −2.0063 24.5584 −2.4662 3.9234 24.5584 0.4221 −2.4273 24.5584 −2.6508 4.3235 24.5584 0.5406 −2.8342 24.5584 −2.8295 4.7091 24.5584 0.6543 −3.2260 24.5584 −3.0016 5.0803 24.5584 0.7648 −3.6024 24.5584 −3.1672 5.4372 24.5584 0.8737 −3.9629 24.5584 −3.3250 5.7804 24.5584 0.9823 −4.3069 24.5584 −3.4731 6.1107 24.5584 1.0871 −4.6192 24.5584 −3.6124 6.4277 24.5584 1.1888 −4.8996 24.5584 −3.7349 6.7177 24.5584 1.2853 −5.1487 24.5584 −3.8400 6.9807 24.5584 1.3724 −5.3678 24.5584 −3.9289 7.2163 24.5584 1.4515 −5.5564 24.5584 −4.0077 7.4388 24.5584 1.5239 −5.7135 24.5584 −4.0723 7.6330 24.5584 1.5888 −5.8464 24.5584 −4.1180 7.7836 24.5584 1.6443 −5.9576 24.5584 −4.1500 7.9054 24.5584 1.6901 −6.0491 24.5584 −4.1698 7.9978 24.5584 1.7268 −6.1223 24.5584 −4.1802 8.0678 24.5584 1.7548 −6.1786 24.5584 −4.1827 8.1071 24.5584 1.7758 −6.2209 24.5584 −4.1812 8.1322 24.5584 1.7931 −6.2562 24.5584 −4.1777 8.1442 24.5584 1.7893 −6.2871 24.5584 −4.1738 8.1490 24.5584

It will be appreciated that the airfoil 105 disclosed in the above scalable TABLE 1 may be non-scaled, scaled up, or scaled down geometrically for use in other or similar turbine/compressor designs. Consequently, the coordinate values set forth in TABLE 1 may be non-scaled, scaled upwardly, or scaled downwardly such that the general airfoil profile shape remains unchanged. A scaled version of the coordinates in TABLE 1 would be represented by X, Y, and Z coordinate values of TABLE 1, with the X, Y, and Z non-dimensional coordinate values converted to inches or millimeters (or any suitable dimensional system), multiplied or divided by a constant number. The constant number may be a fraction, decimal fraction, integer or mixed number.

The disclosed airfoil shape thus may increase reliability and may be specific to the machine conditions and specifications. The airfoil shape provides a unique profile to achieve (1) interaction between other stages in the compressor; (2) aerodynamic efficiency; and (3) normalized aerodynamic and mechanical blade or vane loadings. The disclosed loci of points allow the gas turbine and the compressor or any other suitable turbine/compressor to run in an efficient, safe and smooth manner. As also noted, any scale of the disclosed airfoil may be adopted as long as (1) interaction between other stages in the compressor; (2) aerodynamic efficiency; and (3) normalized aerodynamic and mechanical blade loadings are maintained in the scaled compressor.

The airfoil 105 described herein thus improves overall compressor efficiency. Specifically, the airfoil 105 may provide the desired turbine/compressor efficiency lapse rate (ISO, hot, cold, part load, etc.). The airfoil 105 also meets all aeromechanics, loading and stress requirements.

It should be apparent that the foregoing relates only to certain embodiments of the present application and the resultant patent. Numerous changes and modifications may be made herein by one of ordinary skill in the art without departing from the general spirit and scope of the invention as defined by the following claims and the equivalents thereof. 

We claim:
 1. An article of manufacture having a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y, and Z set forth in scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.
 2. The article of manufacture according to claim 1, wherein the article of manufacture comprises an airfoil.
 3. The article of manufacture according to claim 1, wherein the article of manufacture comprises a rotor blade configured for use with a compressor.
 4. The article of manufacture according to claim 1, wherein the airfoil shape lies in an envelope within +/−5% of a chord length in a direction normal to an airfoil surface location.
 5. The article of manufacture according to claim 1, wherein the number, used to convert the non-dimensional values to dimensional distances, is at least one of a fraction, a decimal fraction, an integer, and a mixed number.
 6. The article of manufacture according to claim 1, wherein a height of the article of manufacture is about 1 inch to about 20 inches.
 7. An article of manufacture having a suction-side nominal airfoil profile substantially in accordance with suction-side Cartesian coordinate values of X, Y, and Z set forth in scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete suction-side airfoil shape, the X, Y, and Z coordinate values being scalable as a function of the number to provide at least one of a non-scaled, scaled-up, and scaled-down airfoil profile.
 8. The article of manufacture according to claim 7, wherein the article of manufacture comprises an airfoil.
 9. The article of manufacture according to claim 7, wherein the article of manufacture comprises a rotor blade configured for use with a compressor.
 10. The article of manufacture according to claim 7, wherein the suction-side airfoil shape lies in an envelope within +/−5% of a chord length in a direction normal to a suction-side airfoil surface location.
 11. The article of manufacture according to claim 7, wherein the number, used to convert the non-dimensional values to dimensional distances, is at least one of a fraction, a decimal fraction, an integer, and a mixed number.
 12. The article of manufacture according to claim 7, wherein a height of the article of manufacture is about 1 inch to about 20 inches.
 13. The article of manufacture according to claim 7, further comprising the article of manufacture having a pressure-side nominal airfoil profile substantially in accordance with pressure-side Cartesian coordinate values of X, Y, and Z set forth in the scalable table, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete pressure-side airfoil shape, the X, Y, and Z values being scalable as a function of the number to provide at least one of a non-scaled, scaled-up, and scaled-down airfoil.
 14. A compressor comprising a plurality of rotor blades, each of the rotor blades including an airfoil having a suction-side airfoil shape, the airfoil having a nominal profile substantially in accordance with suction-side Cartesian coordinate values of X, Y, and Z set forth in scalable TABLE 1, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by a number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete suction-side airfoil shape.
 15. The compressor according to claim 14, wherein the suction-side airfoil shape lies in an envelope within +/−5% of a chord length in a direction normal to a suction-side airfoil surface location.
 16. The compressor according to claim 14, wherein the number, used to convert the non-dimensional values to dimensional distances, is at least one of a fraction, a decimal fraction, an integer, and a mixed number.
 17. The compressor according to claim 14, wherein a height of each rotor blade is about 1 inch to about 20 inches.
 18. The compressor according to claim 14, further comprising each of the plurality of rotor blades having a pressure-side nominal airfoil profile substantially in accordance with pressure-side Cartesian coordinate values of X, Y, and Z set forth in the scalable table, wherein the Cartesian coordinate values of X, Y, and Z are non-dimensional values convertible to dimensional distances by multiplying the Cartesian coordinate values of X, Y, and Z by the number, and wherein X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height, the airfoil profile sections at each Z height being joined with one another to form a complete pressure-side airfoil shape.
 19. The compressor according to claim 18, wherein the pressure-side airfoil shape lies in an envelope within +/−5% of a chord length in a direction normal to a pressure-side airfoil surface location.
 20. The compressor according to claim 18, wherein the number, used to convert the non-dimensional values to dimensional distances, is at least one of a fraction, a decimal fraction, an integer, and a mixed number. 